风力机叶片翼型气动特性数值模拟

针对NACA63-215翼型绕流流动建立了二维可压缩湍流模型,利用商业软件NU-MECA进行了相应的数值模拟计算.湍流粘度分别采用基于RANS的Spalart-Allmaras和Baldwin-Lomax两种湍流模型来处理,得出了雷诺数为3×106时,翼型NACA63-215的升力系数和阻力系数随来流攻角的变化关系及压力分布图,并与试验数据进行对比.研究结果表明:Spalart-All-maras湍流模型比Baldwin-Lomax湍流模型在预测翼型失速后气动性能方面更加有效,Spalart-Allmaras湍流模型在大攻角下较易收敛且计算出的翼型气动性能与试验值更接近.

Numerical simulation on aerodynamic performance of an airfoil for wind turbine

2D physical and mathematical model was built to simulate the flow around NACA63-215 airfoil,then the steady compressible Reynolds-Averaged Navier-Stokes equations were solved numerically and both Spalart-Allmaras and Baldwin-Lomax turbulence model were applied to solve the turbulent viscosity using the CFD commercial software called NUMECA.The coefficients of lift and drag as well as the pressure distribution were concluded with the change of angle of flow attack for airfoil NACA63-215.The comparison between computed results and experimental data showed that predicting results of Spalart-Allmaras turbulence model were closer to the experimental results and can be more effective in predicting aerodynamic performance of airfoil after stalling.